The　aerothermoelastic　characteristics　of　the　supersonic　laminated　cylindrical　shell　are　analyzed,　and　the　active　flutter　control　of　the　aeroelastic　structure　is　also　investigated　using　the　piezoelectric　material.　In　the　structural　modeling,　the　influences　of　the　in-plane　thermal　load　on　the　transverse　deformation　are　taken　into　account.　The　aerodynamic　pressure　is　evaluated　using　the　supersonic　piston　theory.　Hamilton＇s　principle　and　the　Galerkin＇s　method　are　used　to　establish　the　equation　of　motion.　The　proportional　feedback　and　LQG　control　methods　are　applied　to　design　the　controller.　The　aerothermoelastic　analysis　for　the　laminated　cylindrical　shell　is　carried　out　using　the　frequency-　and　time-domain　methods.　The　influences　of　the　ply　angle　on　the　flutter　and　thermal　buckling　properties　are　investigated.　The　active　flutter　control　effects　of　different　controllers　are　compared.　Numerical　simulation　shows　that　the　LQG　controller　is　more　accurate　and　effective　than　the　LQR　and　proportional　feedback　controllers.　(C)　2013　Elsevier　Ltd.　All　rights　reserved.